Panel for an aircraft cabin
阅读说明:本技术 用于飞机机舱的面板 (Panel for an aircraft cabin ) 是由 塔玛拉·布兰科瓦雷拉 彼得·林德 于 2020-04-02 设计创作,主要内容包括:本发明涉及一种用于飞机机舱的面板(1000),所述面板(1000)包括:至少一个层压板(150),所述至少一个层压板(150)包括包括锂化碳纤维(100)的第一层、包括具有阴极锂涂层(200)的碳纤维的第二层、以及介于所述第一层和所述第二层之间的含电解质的隔板(300)中的一者或多者;被设置在所述层压板(150)的外表面上的至少一个压力传感器(50a,50b);以及开关(40),所述开关(40)基于所述压力传感器(50a,50b)的输出来调节施加到所述层压板(150)的电压,从而使得所述面板(1000)膨胀。(The invention relates to a panel (1000) for an aircraft cabin, the panel (1000) comprising: at least one laminate (150), the at least one laminate (150) comprising one or more of a first layer comprising lithiated carbon fibers (100), a second layer comprising carbon fibers having a cathodic lithium coating (200), and an electrolyte-containing separator (300) between the first layer and the second layer; at least one pressure sensor (50a, 50b) disposed on an outer surface of the laminate (150); and a switch (40), the switch (40) adjusting a voltage applied to the laminate (150) based on an output of the pressure sensor (50a, 50b), thereby causing the panel (1000) to expand.)
1. A panel (1000) for an aircraft cabin, characterized in that the panel (1000) comprises:
at least one laminate (150), the at least one laminate (150) comprising one or more of:
a first layer comprising lithiated carbon fibers (100);
a second layer comprising carbon fibers having a cathodic lithium coating (200); and
an electrolyte-containing separator (300), the electrolyte-containing separator (300) being interposed between the first layer and the second layer;
at least one pressure sensor (50a, 50b), the at least one pressure sensor (50a, 50b) being disposed on an outer surface of the laminate (150); and
a switch (40), the switch (40) regulating a voltage applied to the laminate (150) based on an output of the pressure sensor (50a, 50b) to cause the panel (1000) to expand.
2. The panel (1000) of claim 1, further comprising a microcontroller configured to receive an output of the pressure sensor (50a, 50b) and actuate the switch (40).
3. The panel (1000) according to claim 1 or 2, further comprising a power source (30), the power source (30) providing the applied voltage to the laminate (150).
4. The panel (1000) according to any of claims 1 to 3, wherein the cathodic lithium coating (200) comprises LiFePO4。
5. The panel (1000) according to any of claims 1 to 4, further comprising a foam (600) for filling the panel (1000).
6. The panel (1000) of claim 5, further comprising a second laminate (250) and the foam (600) is sandwiched between the first laminate (150) and the second laminate (250).
7. A luggage rack for an aircraft, the luggage rack comprising a panel according to any of claims 1 to 6.
8. A cabin lining for an aircraft, comprising a panel according to any one of claims 1 to 6.
9. A method for filling a gap at a two-panel joint between a panel (1000) of an aircraft cabin and a cabin element (20), the first panel comprising a laminate (150), the laminate (150) comprising a first layer of lithiated carbon fibers (100), a second layer of carbon fibers having a cathodic lithium coating (200), and an electrolyte-containing separator (300) disposed between the first layer and the second layer, the method comprising:
-detecting a gap between the panel (1000) and the nacelle element (20) with a pressure sensor (50a, 50 b); and
-applying a voltage to the laminate (150) based on the output of the pressure sensor, which causes the panel (1000) to expand and fill the gap.
10. The method of claim 9, further comprising:
-detecting contact between the panel (1000) and the nacelle element (20) with the pressure sensor (50a, 50b) in response to the panel (1000) expanding and filling the gap; and
-terminating the voltage applied to the laminate (150) based on the output of the pressure sensor.
11. The method of claim 9 or 10, further comprising:
-regulating the voltage applied to the laminate (150) with a switch (40); and
-actuating the switch (40) with a microcontroller receiving an output from the pressure sensor (50a, 50 b).
12. The method of any of claims 9-11, further comprising applying the voltage to the laminate (150) using a battery (30).
13. The method of any of claims 9 to 12, further comprising using a second panel (1000) as an energy storage for applying the voltage to the laminate (150).
14. The method of any of claims 9 to 13, further comprising orienting the lithiated carbon fibers (100) of the laminate (150) transverse to the two-panel joint.
15. The method of any of claims 9 to 13, further comprising orienting the lithiated carbon fibers (100) of the laminate (150) longitudinally to the two-panel joint.
Technical Field
The invention relates to a panel structure for an aircraft cabin.
In particular, it is an object of the present invention to provide an adjustable panel for aircraft cabins based on the piezoelectric-chemical-electric (piezo-electric) properties of lithiated carbon fibers for the automatic filling of gaps and a related method for filling gaps between panel cabins.
Background
Aircraft cabins are equipped with panels to cover elements such as insulation, pipes and wires. Panels known as "liners" are typically of a sandwich design with a foam or honeycomb core that may include a cover layer of carbon fiber reinforced polymer GRFP or CFRP. The joint between two adjacent panels often shows visible gaps due to geometry, temperature and installation reasons, as shown in figure 1 of the present invention. Fig. 1 includes a
Furthermore, fig. 2 shows an example of a
Therefore, there is a need to find a solution that avoids these undesired gaps and does not require, for example, changing the positioning of the nacelle panels and/or using gap fillers as described before. The present invention aims to solve this problem.
Disclosure of Invention
Electrochemical cells store electrical energy due to spontaneous chemical reactions that occur internally. An electrochemical cell consists of two half-cells (half cells) connected by a salt bridge. Lithium ion batteries consist of two distinct electrodes separated from each other by an electrolyte, which is an ionic conductor but an electronic insulator. The free energy associated with the transfer of electrons around the external circuit and lithium ions ("li-ions") between the two intercalation electrodes in the battery is related to the difference in the chemical potentials of the lithium in the two electrodes.
Lithium batteries include three major components. First, an anode, which releases electrons to an external circuit upon discharge and is oxidized during the electrochemical reaction. Most commercial batteries currently employ a carbon/graphite based electrode as the anode. Second, a cathode that accepts electrons from an external circuit upon discharge and is reduced during the electrochemical reaction. The cathode is typically a transition metal oxide or phosphate. Third, an electrolyte (an ionic conductor but an electronic insulator) that separates the two electrodes and provides a medium for charge transfer between the anode and the cathode within the cell. The electrolyte is typically a non-aqueous inorganic solvent containing a dissolved lithium salt, such as LiPF in propylene carbonate6(lithium hexafluorophosphate).
In the charged state of the battery, the positive electrode and the negative electrode are oxidized, lithium ions are deintercalated from the layered lithium intercalation host (de-intercalated), pass through the electrolyte, and are intercalated between graphite layers through an electrochemical reduction reaction at the negative electrode. Intercalation involves the reversible insertion of guest atoms into a solid host structure without causing significant destruction of the host material.
An example of a lithium battery is a lithium iron phosphate (LiFePO) battery, also known as an LFP battery ("LFP" stands for "lithium iron phosphate"), which is a rechargeable battery, in particular a lithium ion battery, using LiFePO as a cathode material and a graphitic carbon electrode with a metallic current collector grid as an anode.
Fig. 3 shows an electrochemical LiFePO cell comprising carbon fibers 100 (anode) with lithium ions attached, a cathode (such as with LiFePO)4The cathode coating carbon 200), a
It has been found that lithiated carbon fibers (e.g., with LiFePO)4Carbon) to obtain piezoelectric-chemical-electrical characteristics. Lithiation is defined as the incorporation of lithium into an electrode in a lithium ion battery. Fig. 4 shows the piezoelectric-chemical-electrical effect of the lithiated
It has also been found that the diameter of the carbon fiber can be increased and thus the carbon fiber can "swell", as shown in fig. 5, when the potential of the counter electrode (counter electrode) is increased, the lithiated carbon fiber has a
It is therefore an object of the present invention to provide an adjustable panel for aircraft cabins, which automatically fills the gaps on the basis of the above-mentioned piezoelectric-chemical-electrical properties of lithiated carbon fibers, and an associated method for filling the gaps between panel cabins.
This is achieved by providing a panel integrated with carbon fibre layers which may be lithiated by means of an electrode. The counter or auxiliary electrode provides a means for applying an input potential to the working electrode (i.e., the carbon fibers). As long as the gap with the adjacent panel (i.e., the gap between the two joined panels) is detected by the pressure sensor, the lithiated carbon fiber layer of the panel can be expanded by controlling the potential of the counter electrode until the gap closes. At the same time, the charged panel may be used as an energy storage battery. The proposed panel for an aircraft cabin comprising lithiated carbon fibers is therefore multifunctional, achieving a structural function, a gap-filling function, and an energy storage function since the expanded fibers can simultaneously store energy. Thus, with the proposed panel, closing joints in the nacelle by changing the positioning of the nacelle panels or by filling gaps with "gap fillers" is avoided. Furthermore, automatic gap control and filling allows continuous correction of the effects of temperature, pressure, etc.
Accordingly, a first aspect of the invention is a panel for an aircraft cabin, the panel comprising at least one laminate comprising at least: a first layer comprising lithiated carbon fibers, a second layer comprising carbon fibers having a cathodic lithium coating, and an electrolyte-containing separator interposed between the first layer and the second layer. In some examples, the panel may include an upper laminate having two layers of lithiated carbon fibers, two separators, and a single layer including carbon fibers with a cathodic lithium coating shared between two adjacent separators. Furthermore, the same panel may comprise a lower laminate having the same five layers as the upper laminate.
The panel may include one or more pressure sensors disposed on an outer surface of the laminate. Further, the panel includes a switch for adjusting a voltage applied to the laminate. In this regard, the pressure sensor is configured to provide an output for use by the switch. The output may indicate that a gap is detected at the junction between the panel and the other nacelle element. Thus, the switch may regulate the voltage applied to the laminate based on the output from the pressure sensor. The applied voltage may cause the panel to expand so that the panel may fill the gap. The panel also includes a microcontroller integrated with the switch and that actuates the switch based on an output signal received from the pressure sensor. The panel also includes a power source that provides an applied voltage to the laminate. In some examples, the voltage source is not included in the panel. In other examples, the voltage source is another panel according to the invention.
In some examples, the cathodic lithium coating may include LiFePO4. The panel may further comprise a foam sandwiched between the first laminate and the second laminate.
Another aspect of the invention relates to a luggage rack for an aircraft comprising the proposed panel and a cabin lining comprising the proposed panel. This means that the proposed panel can be integrated into any element of the aircraft cabin for gap filling and/or energy storage purposes.
In another aspect of the invention, a method is presented for filling a gap between a joint of two panels (two-panel) comprising a panel according to the first aspect of the invention and a cabin element of an aircraft, a first panel comprising a laminate comprising a first layer of lithiated carbon fibers, a second layer of carbon fibers having a cathodic lithium coating, and an electrolyte-containing separator disposed between the first layer and the second layer, the method comprising detecting the gap between the panel and the cabin element with a pressure sensor, and applying a voltage to the laminate based on an output of the pressure sensor, the applied voltage expanding the lithiated carbon fibers of the first layer and the panel. This expansion causes the panel to fill the gap. The voltage applied to the laminate may be regulated with a switch.
The method further comprises the steps of: after filling the gap with the panel, detecting contact between the panel and the nacelle element with the pressure sensor, and terminating the voltage applied to the laminate by actuating the switch based on an output from the pressure sensor. The switches in the panel may be actuated using a microcontroller integrated with the switches and configured to receive an output from the pressure sensor. The pressure sensor may for example be a piezoelectric sensor. The output of the pressure sensor may be an output voltage, wherein, for example, a low voltage indicates detection of a gap at the joint between the proposed panel and the nacelle element, and a high voltage indicates detection of contact between the panel and the nacelle element in response to mechanical stress to which the pressure sensor is subjected during contact.
The method further comprises using the battery as an energy storage for applying a voltage to the laminate in the panel or using another panel according to the invention as an energy storage for applying a voltage to the laminate. As previously mentioned, the laminate is an electrochemical cell that can be used for energy storage. The method further includes positioning or orienting the lithiated carbon fibers of the laminate parallel to the two-panel joint and/or positioning the lithiated carbon fibers of the laminate perpendicular to the two-panel joint. Any distribution of fibers may be used in order to cause expansion of the panels in the longitudinal or transverse direction with respect to the joint.
Drawings
The foregoing description, for purposes of explanation and limitation, includes some non-limiting figures that schematically illustrate practical embodiments for the sole purpose of providing examples.
Fig. 1 shows a joint between two adjacent panels in an aircraft cabin.
Fig. 2 shows a joint between a luggage rack and a crown lining in an aircraft cabin.
Fig. 3 shows an electrochemical LiFePO cell.
Fig. 4 shows the piezoelectric-chemical-electrical effect of lithiated carbon fibers.
Fig. 5 shows the "expanded" diameter of the lithiated carbon fiber.
Fig. 6 shows a panel for an aircraft cabin according to the invention.
Fig. 7A shows a panel for an aircraft cabin according to the invention during the expansion phase.
Fig. 7B shows a panel for an aircraft cabin according to the invention after the expansion phase.
Fig. 8 shows a panel according to the invention with lithiated carbon fibers oriented transverse to the joint.
Detailed Description
Fig. 6 shows an example of a
The laminate 150, 250 also includes a second electrolyte-containing
Further, the
Further, the
The
Fig. 7A shows the
In the described case, the
Fig. 7B shows the
Fig. 8 shows a
Although reference has been made to a particular embodiment of the invention, it is apparent to a person skilled in the art that the panel for an aircraft cabin described herein is susceptible to numerous variations and modifications, and that all the details mentioned may be substituted by other technically equivalent elements without departing from the scope of protection defined by the appended claims.
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